GB679586A - Automatic steering system - Google Patents

Abstract

679,586. Automatic pilots. BENDIX AVIATION CORPORATION. May 26, 1950 [June 23, 1949], No. 13345/50. Class 38 (iv). In an automatic pilot, the ailerons are controlled by the craft heading detector and the rudder by deviations from the dynamic vertical displacement plus rate of yaw to prevent side slip or skidding. Rudder control, Fig. I.-As shown, a pendulum 11 mounted forward of the craft CG to swing athwartships responds to dynamic vertical displacement (a persistent low-frequency signal) and yaw acceleration (a non-persistent higher frequency signal). The output from the pendulum pick-off 13 is fed in part to a selective ball-and-disc type integrator unit 17 to provide a yaw-rate signal, and in part to a thermal delay low-pass filter unit 42 (such as that described in Specification 679,560) which passes only the vertical error signal. These signals appearing at potentiometers 40, 62 respectively are connected in series to the rudder servo amplifier 74 together with the rudder displacement signal from pick-off 67 in a conventional manner. Alternatively the pendulum casing may be filled with damping oil, in which case the required yaw rate plus vertical displacement signal is obtained directly from the pendulum pick-off, Fig. 2 (not shown), or the vertical component may be obtained from a damped pendulum, or an undamped pendulum at the craft CG, and the rate of yaw signal obtained from a gyro, Fig. 3 (not shown). Aileron control.-The conventional aileron servo system is fed from signal detectors responsive to rate of bank, roll displacement, course setter, compass and radio track, Fig. 4. not shown.